16results about How to "Improve flight performance" patented technology

The utility model provides a freight unmanned plane relates to unmanned plane technical field, including fuselage for loading goods, the fuselage tail lower portion is equipped with rear aircraft wheel, rear aircraft wheel is connected with the fuselage through support rod, rear wing is located the fuselage tail upper portion and has upper reflex angle, front wing is located the fuselage head lower portion and has lower reflex angle, the front wing both sides lower portion is equipped with front aircraft wheel, tail push propeller is located the fuselage tail, vertical propeller is located the fuselage both sides, wherein, tail push propeller drives through the fuselage upper oil dynamic piston engine, vertical propeller drives through fuselage upper motor. A freight unmanned plane in the utility model, solved the problem that the prior art lacks a freight unmanned plane capable of stable vertical take-off and landing and long range and large load.

This invention belongs to the field of variable wing technology and discloses a lightweight integrated aerodynamic drive system and a deformable wing. The aerodynamic drive system includes: a double-acting cylinder integrated with the valve bodies of a normally open and normally closed electromagnetic directional valve via a cylinder head; a combined valve comprising an inflation valve and a pressure reducing valve; the inflation valve is located above the pressure reducing valve, with its valve body integrated with the pressure reducing valve's valve body, and its outlet flow channel directly connected to the pressure reducing valve's inlet flow channel; the pressure reducing valve is located on the top of the front cylinder head of the double-acting cylinder, and is connected to the normally open electromagnetic directional valve via a gas-sealed connection, directly docking with a gas cylinder. This system combines optimized gas path design and hardware integration, integrating energy and drive functions, resulting in a compact and lightweight structure. It can adapt well to the requirements of limited installation space, significantly improving the system's adaptability to various operating conditions, thereby enhancing the aircraft's flight performance.

The application belongs to the field of insect breeding, and specifically discloses application of citric acid or capric acid in improving flight ability of irradiated sterile male codling moth, wherein the codling moth is fed with a sucrose solution containing 4 mM citric acid or a sucrose solution containing 250 mu M capric acid within 24 hours after the irradiated male codling moth emerges from the cocoon. Compared with the prior art, the application proves that the feeding treatment of citric acid or capric acid can improve the flight ability of the irradiated sterile male codling moth, and further improve the mating success rate of the sterile male codling moth and the control effect on the population.

The invention discloses a fixed time increment fault-tolerant control method for a control surface mixed fault aircraft. The method comprises the following steps: analyzing the fault type and performance of an aircraft control surface; modeling a control surface fault aircraft; improving the design of a tracking differentiator; designing an incremental dynamic inverse control law; and designing a fixed time increment dynamic inverse fault-tolerant controller. The control method provided by the embodiment of the invention is low in cost and simple in structure, can realize accurate acquisition of the angular acceleration signal and noise filtering, reduces hardware consumption of the angular acceleration sensor, and has a practical engineering application prospect; the robustness is high, and stable control and instruction tracking of the aircraft under the control surface mixed fault can be achieved; the method is high in convergence speed and good in steady-state performance, can guarantee that the faulty aircraft quickly recovers to be stable in a fixed time and accurately tracks the instruction, and effectively improves the flight performance of the faulty aircraft.

This application provides a compound variable-pitch propeller system and control method based on circulation control, relating to the field of aviation technology. The compound variable-pitch propeller system based on circulation control includes: a dual-rotor variable-pitch motor, which is disposed in the propeller hub. The dual-rotor variable-pitch motor includes a first rotor and a second rotor. The first rotor is connected to an inner worm gear, which is connected to a variable-pitch mechanism. The second rotor is connected to an outer worm gear, which is connected to a control surface deflection mechanism. The propeller blades include fixed blades and movable control surfaces. The fixed blades are connected to the propeller hub, and the movable control surfaces are rotatably connected to the fixed blades. The propeller blades have jet slits. A transmission mechanism connects the control surface deflection mechanism and the movable control surfaces for the deflection motion of the movable control surfaces, thereby improving the efficiency and adaptability of the propeller and optimizing flight performance.

The aerodynamic layout comprises a fuselage, wings and an empennage, the wings are installed on the fuselage, the empennage is connected with the wings, the wings comprise a middle wing, outer wings and winglets, the middle wing is connected to the upper end of the middle of the fuselage, the outer wings are symmetrically arranged on the two sides of the middle wing, the winglets are arranged on the edges of the outer wings, the plane shape of the middle wing is rectangular, and the plane shape of the middle wing is rectangular. The plane shape of the outer wing is trapezoid, the sweepback angles of 1 / 4 chord lines of the middle wing and the outer wing are both 0 degree, the dihedral angle of the middle wing is 0 degree, the dihedral angle of the outer wing is 0.5 degree, the empennage comprises a vertical tail and a horizontal tail, and the vertical tail is connected to the wings and arranged behind the fuselage. A stable laminar flow field can be formed in a low-speed cruising state through the combined design of specific structures of the rectangular middle wing and the trapezoidal outer wing, wingspan loads are distributed in an oval trend through the trapezoidal design of the outer wing, induced resistance can be reduced by combining the structural design of the wingtip winglet, and additional resistance caused by the sweepback angle is eliminated through the design that the sweepback angle is 0 degree.

The utility model discloses an unmanned aerial vehicle for agriculture and forestry environment monitoring, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle mounting base, a mounting shell is mounted at the top end of the unmanned aerial vehicle mounting base, a fixing support is mounted in the mounting shell, a fixing plate is fixedly connected to the middle of the fixing support, and a guide sliding rail is arranged at the top end of the fixing plate; the outer wall of the fixed support is slidably connected with a plurality of moving blocks, the top end of each moving block is rotatably connected with a connecting rod, the adjacent ends of the connecting rods are rotatably connected, the ends, close to the fixed plate, of the two connecting rods are slidably connected with the top end of the fixed plate through guide sliding rails, and the bottom end of each moving block is connected with a cooling fin. An electric motor is mounted on one side of the fixed bracket; according to the unmanned aerial vehicle, when the unmanned aerial vehicle is patrolled in different flight states through the adjusting assembly, the contact area between the cooling fins and air is reasonably switched, and the cooling efficiency is improved.

The present application relates to a kind of micro aircraft low-speed lift increasing wrinkle airfoil, including main wing, wind speed detection sensor, shape memory alloy wire, direct current power supply, remote control machine, the main wing is the wrinkle wing profile structure with lift increasing effect, the wind speed detection sensor is installed on main wing and the wind speed signal detected is passed to remote control machine, the shape memory alloy wire is electrically connected with direct current power supply, the shape memory alloy wire and direct current power supply are installed on main wing, the direct current power supply is connected with remote control machine and is controlled by remote control machine, the on-off electricity situation of shape memory alloy wire and direct current power supply is controlled by remote control machine, make main wing switch between wrinkle wing type and flat plate wing type.The present application can significantly improve the lift of micro aircraft wing, has the advantages such as controllable deformation, reliable structure, stable driving and low energy consumption.

The embodiment of the utility model provides a battery device, an energy storage device and an electric device. The battery device comprises a battery monomer and a phase change piece, the battery cell includes a pressure relief mechanism. The multiple phase change pieces are stacked in multiple layers in the first direction to form a stacked body, the stacked body and the pressure relief mechanism are oppositely arranged in the first direction, each phase change piece comprises a shell and a phase change material, a containing cavity is formed in the shell, the phase change materials are stored in the containing cavity, and the shell can be broken under the heat effect of emissions discharged by the pressure relief mechanism to release the phase change materials; and the other peripheral phase change pieces are displaced towards the position of the cracked phase change piece due to the loss of the support of the cracked shell. According to the battery device provided by the embodiment of the invention, after part of the phase change pieces in the stack body are broken under the heat action of the emissions sprayed out by the pressure relief mechanism, other phase change pieces can generate displacement to fill gaps generated by the broken phase change pieces, so that the temperature of the emissions can be better reduced.

The application relates to a variable sweep telescopic wing structure, which comprises a wing platform and a wing assembly, the wing assembly comprising a first wing and a second wing, a first driving assembly, a rotating assembly and a lifting shaft, the rotating assembly comprising a first rotating shaft and a second rotating shaft which are connected in parallel on the wing platform, the first rotating shaft being coaxially sleeved on the lifting shaft, the first rotating shaft being fixedly matched with the lifting shaft in the circumferential direction and being slidably matched with the lifting shaft in the axial direction, the first wing being connected at the top of the lifting shaft, the second wing being connected at the top of the second rotating shaft, and the first wing and the second wing both being telescopic structures, the first driving assembly being transmissionally connected with the first rotating shaft and the second rotating shaft to drive the first rotating shaft and the second rotating shaft to rotate and drive the lifting shaft to lift. The structure can realize wing unfolding and folding with any sweep angle, increase the stability and flexibility of the aircraft, be telescopic to change the wing area, adapt to different flight states, improve the wing efficiency and improve the flight performance.

The invention relates to the technical field of aviation aircraft design, and discloses a variable camber wing based on a bistable composite material structure driving multi-section rotation, which comprises a wing leading edge structure, a multi-section rotation rigid skin, an internal truss structure connected with the multi-section rotation rigid skin, a bistable composite material driving structure and a transmission mechanism, the bistable composite material driving structure is arranged between the rigid skin hinge and the transmission mechanism; and the transmission mechanism is arranged between the truss structure in the rigid skin and the sliding chute of the wing leading edge structure. The control precision and reliability are improved through relative change of the three rigid wings, and the problems that in the prior art, the structure is complex, the weight is large, the actuation efficiency is low, and the bearing capacity is low are solved.

The application discloses a kind of unmanned plane recycling methods, comprising the following steps: ground station system obtains the position information of fixed-wing unmanned plane, keeps the flight state of fixed-wing unmanned plane, and issues take-off instruction to multi-rotor unmanned plane;Multi-rotor unmanned plane tracks the navigation point of fixed-wing unmanned plane, shortens the relative distance between multi-rotor unmanned plane and fixed-wing unmanned plane;Adjust the flight parameters of multi-rotor unmanned plane, keep the distance difference of multi-rotor unmanned plane and fixed-wing unmanned plane in height direction;Adjust the relative motion distance between multi-rotor unmanned plane and fixed-wing unmanned plane, and carry out docking recycling;Close the power system of fixed-wing unmanned plane, control multi-rotor unmanned plane to land to preset place.The application can well utilize multi-rotor unmanned plane to realize the recycling of fixed-wing unmanned plane in the air.The application also discloses a kind of unmanned plane recycling system, ground station system, unmanned plane.

The application provides a band type unlocking separation device and relates to the technical field of aerospace. The band type unlocking separation device comprises a band structure, the band structure comprises a band body with elasticity and a clamping block, the clamping block limits a first cylinder structure and a second cylinder structure through a limiting groove, the band body is used for elastic deformation to abut against a first limiting protrusion and a second limiting protrusion through the clamping block, and the band type unlocking separation device further comprises a position keeping structure connected with both ends of the band body to keep the band body in an elastic deformation state. The both ends of the band structure are limited through the position keeping structure, and the first cylinder structure and the second cylinder structure are limited through the clamping block. When unlocking and separating, the position keeping structure is released from the limitation, the band structure is contracted and deformed, and unlocking and separation are realized. The application can be arranged on an inner wall and is more suitable for scenes with higher requirements on the smoothness of the outer surface of the cylinder structure.

This invention discloses a method for calculating the modal characteristic parameters of a connected-wing aircraft using nonlinear flight mechanics fitting, relating to the field of flight mechanics technology. The method includes the following steps: S1, preparation for full nonlinear modal characteristic analysis of the connected-wing aircraft, including initial flight state parameters, aerodynamic database, disturbance signals, time scale, and a full nonlinear flight dynamics model; S2, solving the nonlinear dynamics simulation of the connected-wing aircraft using an iterative simulation method; S3, fitting the modal characteristic parameters using the least squares method based on the simulation results to obtain the final processed result. This invention's method for calculating the modal characteristic parameters of a connected-wing aircraft using nonlinear flight mechanics fitting improves the accuracy of flight performance analysis, enhances the reliability of nonlinear dynamics simulation, and provides design basis and technical support for aircraft design and flight control.

The utility model discloses an unmanned aerial vehicle charging station with a damping structure, which comprises a cab, a frame is mounted at the bottom of the cab, a vehicle body is arranged in the frame, a correcting component is mounted in the vehicle body, a damping component is mounted in the vehicle body, and the damping component is mounted in the damping component. A sliding rail is fixedly connected to the back face of the cab, an electric sliding block is arranged in the sliding rail, a folding frame is installed on the outer side of the electric sliding block, and a cover plate is installed at one end of the folding frame. According to the unmanned aerial vehicle charging station with the damping structure, a three-stage buffering damping design is adopted through the damping assembly, a three-dimensional damping protection system is formed through the synergistic effect of the buffering rods, the buffers and the damping springs, and when an unmanned aerial vehicle lands, the buffering rods made of high-strength alloy firstly make contact with a vehicle body, and the buffering rods make contact with the vehicle body; impact force is primarily dispersed through the unique honeycomb-shaped buffering platform.